US20040154309A1 - Turbine engine - Google Patents

Turbine engine Download PDF

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Publication number
US20040154309A1
US20040154309A1 US10/470,361 US47036104A US2004154309A1 US 20040154309 A1 US20040154309 A1 US 20040154309A1 US 47036104 A US47036104 A US 47036104A US 2004154309 A1 US2004154309 A1 US 2004154309A1
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United States
Prior art keywords
reaction member
vanes
engine according
mixture
fuel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
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US10/470,361
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English (en)
Inventor
Gill Bernard
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ACADEMY PROJECTS Ltd
Original Assignee
ACADEMY PROJECTS Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Assigned to ACADEMY PROJECTS LIMITED reassignment ACADEMY PROJECTS LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GILL, BERNARD
Publication of US20040154309A1 publication Critical patent/US20040154309A1/en
Priority to US11/418,844 priority Critical patent/US20070068135A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • F02C3/09—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage of the centripetal type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/442—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps rotating diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2200/00—Mathematical features
    • F05D2200/10—Basic functions
    • F05D2200/11—Sum

Definitions

  • the present invention relates to engines and relates particularly, but not exclusively, to engines used in the generation of electricity.
  • FIG. 1 An example, of an engine used in the generation of electricity is shown in FIG. 1.
  • the engine known as a gas turbine engine, comprises a compressor 10 which compresses air drawn in through an air inlet 11 .
  • the compressed air is heated in a heat exchanger 12 , taking advantage of the hot exhaust gases of the engine.
  • the heated compressed air is mixed with fuel from a fuel inlet 13 and is burnt in a combustion chamber 14 where the volume of gas significantly increases causing the velocity at which the gas is moving to also significantly increase.
  • the fast moving gas is directed through a turbine 15 which is caused to rotate and the excess hot gas is exhausted via heat exchanger 12 .
  • the rotation of turbine 15 drives a shaft 16 which is connected to compressor 10 and provides the power for compression of the air within compressor 10 .
  • the shaft is also connected to a generator 17 which generates electricity.
  • an engine comprising:
  • a housing having at least one inlet and at least one exhaust outlet;
  • a compression fan adapted to rotate in a first sense to cause compression of a fuel and air mixture
  • reaction member mounted substantially coaxially with said compression fan and comprising a plurality of vanes, wherein the reaction member is adapted to receive said compressed fuel and air mixture from said compression fan and in use said fuel and air; mixture is burnt between said vanes and gases produced by said burning are vectored to cause said reaction member to rotate in a second sense opposite to said first sense.
  • Engines which are typically used for such purposes at present include the internal combustion engine, generally of the petrol or diesel type.
  • the above described invention provides the advantage over these types of engine that there is no conversion of the linear motion of pistons in to the rotary motion of a drive shaft with the inherent losses in energy which will occur. Furthermore there is no requirement for a continuously operating ignition timing mechanism or complex water cooling system which also reduces the energy losses of the engine of the present invention.
  • said fuel and air mixture are further compressed within said reaction member.
  • said further compression occurs by diffusion of said mixture within said reaction member.
  • said further compression occurs by ram compression of said mixture within said reaction member.
  • said compression fan discharges said mixture in a direction substantially tangential to a circle defined by the rotation of vane tips of the vanes of the compression fan.
  • said fuel and air mixture is received within said reaction member at a velocity relative to the reaction member substantially equal to the sum of the velocities of the compression fan vane tips and the reaction member at substantially the same radius.
  • the engine further comprises at least one turbine member for driving said compression fan.
  • At least one said turbine member is driven by exhaust gases from said reaction member.
  • said fuel and air mixture is mixed prior to entry into the engine through the or each inlet.
  • the cross-sectional area measured in a circumferential direction, of the space defined by two adjacent vanes, increases as the radial distance from the axis of the reaction member increases, to a maximum substantially half way along the length of said vanes, and then decreases as said radial distance further increases.
  • each section of the reaction member acts in a similar manner to a ram-jet. That is, that as the fuel air mixture is forced at high velocity from the compression fan into the reaction member it is caused to slow down by the increasing volume between two vanes, which in turn increases the pressure of the fuel air mix.
  • the fuel air mixture is burnt and the hot expanding combustion gases continue through the passage area between adjacent vanes which vector or direct the combustion gases through a nozzle formed by the now converging adjacent vanes.
  • the direction of the expelled gas is tangential to the reaction member radius thereby causing the tangential jet reaction which rotates the reaction member in the second sense.
  • reaction member further comprises a flame grid.
  • the reaction member By providing the reaction member with a flame grid the advantage is provided that the grid acts as a bluff body, which causes the velocity of the fuel air mix immediately behind the flame grid to be less than the flame speed relative to the flame grid. As a result, the combustion of the fuel air mix can be controlled at the flame grid.
  • the flame grid is located at a position along the vanes where the cross-sectional area defined by adjacent vanes, is at its greatest.
  • the advantage is provided that the fuel air mix is burnt at the point of slowest gas speed and as a result highest pressure.
  • the decrease in speed and increase in gas pressure results from the increase in cross-sectional area between the vanes.
  • vanes are adapted to reduce a cross-sectional area, measured in a circumferential direction, of the space defined by two adjacent vanes, decreases as the radial distance from the axis of the reaction member increases, to a minimum cross-sectional area, thereby substantially defining the flame front, before increasing.
  • reaction member further comprises at least one outer supporting member which supports said vanes along at least some of their length.
  • said reaction member comprises two said outer supporting members attached to said vanes along opposing edges of said vanes.
  • vanes are supported substantially along their whole length.
  • said outer supporting members extend to at least partially cover the compression fan.
  • vanes at their smallest radial distance from the axis of the reaction member are at an angle substantially tangential to the outer radius of the compression fan.
  • said housing has at least one further inlet, adapted to allow a flow of cooling air to be entrained between said housing and said reaction member.
  • said reaction member has further vanes extending outside of the supporting members of the reaction member, and adapted to provide the flow of cooling air.
  • said further vanes are adapted to provide said flow of air at a pressure substantially equivalent to a pressure of combustion products of the burning of the fuel and air mixture immediately adjacent a maximum radius of said reaction member
  • FIG. 1 is a schematic cross-sectional view of a gas turbine engine of the prior art
  • FIG. 2 is a cross-section view of an engine of a first embodiment of the present invention
  • FIG. 3 is a cross-sectional view, along the line A-A, of the engine of FIG. 2;
  • FIG. 4 is a cross-sectional view of an engine of a second embodiment of the present invention.
  • FIG. 5 is a cross-sectional view of the engine of FIG. 4.
  • FIG. 6 is a cross-sectional view of an engine of a third embodiment of the present invention.
  • an engine 30 comprises a housing 32 having inlets 34 therein.
  • Engine 30 also has a compression fan 36 coaxially mounted with reaction member 38 .
  • Compression fan 36 is mounted on and fixed with respect to hollow axle 40 and reaction member 38 is mounted on and fixed-with respect to axle 42 .
  • axle 40 Mounted within axle 40 is a further axle (or free spindle) 44 .
  • Free spindle 44 is free to rotate relative to axle 40 and compression fan 36 , and relative to axle 42 and reaction member 38 , by virtue of its mounting on first bearing assemblies 46 and second bearing assemblies 48 .
  • Axle 42 is mounted on bearings 50 .
  • Casing 32 extends around reaction member 38 to form volute 52 and extends to form a further volute which extends around nozzle ring 53 .
  • Adjacent to nozzle ring 53 is turbine wheel 54 which is connected to compression fan 36 via axle 40 .
  • the engine 30 further comprises exhausts 56 .
  • Reaction member 38 comprises vanes 60 , flame grid 62 and supporting members in the form of side casings 64 . Adjacent pairs of vanes 60 define sections 66 which are themselves divided by flame grid 62 into diffusion zones 68 and combustion zones 70 . Each vanes 60 may be divided into two sections, 60 a and 60 b, on either side of the flame grid 62 .
  • the compression fan 36 has vanes 72 which have vane tips 74 .
  • FIG. 2 is a view along the line B-B in FIG. 3.
  • a mixture of fuel and air enters engine 30 via inlets 34 .
  • the mixture is drawn into compression fan 36 which causes an increase in the pressure of the mixture.
  • From the compression fan 36 the mixture is directed towards the reaction member 38 .
  • the rotation of the compression fan 36 causes the vane tips 74 of vanes 72 to define a circle (which as shown in FIG. 3 approximates to the outer rim of the compression fan)
  • the mixture is directed by the compression fan substantially tangential to this circle. Because the compression fan 36 is rotating in a first sense or direction D (as shown in FIG.
  • the velocity of the fuel and air mixture entering the reaction member 38 , relative to the reaction member 38 is approximately the sum of the external rim velocity of the compression fan 36 and the internal rim velocity of the reaction member 36 .
  • the reaction member 38 which encloses the compression fan 36 , receives the mixture into the diffusion zone 68 between adjacent pairs of vanes 60 .
  • the geometry of the diffusion zone 68 is designed to receive the mixture at high velocity and efficiently exchange that velocity for pressure. For example, if the mixture is travelling at subsonic speeds, as the mixture enters the reaction member 38 it firstly enters the diffusion zones 68 between adjacent pairs of vanes 60 . As the mixture moves radially outwards through the reaction member 38 , the volume into which the mixture is moving increases, due to the radial divergence of the vanes 60 . This increase in volume is exaggerated as the side casings 64 of the reaction member 38 diverge from the point of entry of the mixture.
  • This increase in volume causes the velocity at which the mixture is travelling to reduce, which in turn increases the pressure of the mixture.
  • the mixture if the mixture is travelling at supersonic speeds, as the mixture enters the reaction member 38 it firstly enters the diffusion zones 68 between adjacent pairs of vanes 60 . As the mixture moves radially outwards through the reaction member 38 , the volume into which the mixture is moving decreases, due to the geometry of the vanes 60 . This decrease in volume causes an increase in the pressure of the mixture.
  • the grid 62 consists of a perforated sheet of a material which can withstand the temperatures experienced within the reaction member 38 .
  • the flame grid 62 acts as a bluff body. As the mixture passes through the perforations it is caused to increase its velocity relative to the velocity of the mixture immediately before flame grid 62 . Once through the perforations in the flame grid the mixture becomes turbulent and decreases its velocity thereby filling the space immediately behind the material (non-perforated part) of the flame grid 62 .
  • Flame grid 62 marks a boundary at which combustion of the fuel air mixture occurs.
  • the combustion takes place in the turbulent zone immediately behind the flame grid and is maintained there by the flame grid as a result of the increase in the velocity of the mixture as it passes through the perforations. This increased velocity must be greater than the flame speed of the fuel air mixture in order to retain the flame front at the flame grid 62 .
  • the combustion of the mixture causes a rapid increase in the gaseous volume contained within the combustion zone 70 of each section 66 of reaction member 38 . These gases continue through the combustion zones 70 and upon exit from the reaction member 38 apply a reaction force at a radius to the axis of the reaction member 38 turning it in an opposite direction (or sense) to the direction of movement of compression fan 36 .
  • the geometry of the combustion zone 70 is designed to suit the expanding combustion gases.
  • the distance between the side casings 64 may be varied or the curvature of the vane 60 may be varied or a combination of both so as to control and direct the combustion gases to the exit of the combustion zone 70 of the reaction member 38 where the reaction force is generated.
  • the curvature of the vanes 60 and the shape of the sides casings 64 are such that they create nozzles at the exit of the combustion zones 70 . These nozzles are sized so as to optimise the velocity of the gases as they exit the reaction member 38 .
  • the nozzles are angled, by curvature of the vanes 60 so as to cause the gases to exit at an optimum angle thereby applying an optimum torque to the reaction member.
  • reaction member 38 The external surfaces of reaction member 38 are cooled by air drawn in through air inlets 58 .
  • the cooling air is entrained into the gas stream at the maximum radius of the reaction member 38 .
  • axle 42 is rotated. This can occur by the application of electrical power to the generator attached to axle 42 , the generator thereby acting as an electric motor and causing the axle 42 to turn.
  • another starter motor can be used to cause the rotation of axle 42 .
  • the resulting rotation of axle 42 causes the rotation of reaction member 38 which draws the fuel air mixture through inlets 34 . Once the velocity of the fuel air mixture exiting the reaction member 38 is marginally greater than the flame speed of the mixture, the mixture is ignited.
  • the combustion gases are directed through the turbine which drives the turbine wheel 54 which drives the compression fan 36 .
  • the speed of the reaction member 38 is then adjusted so that the flame flashes back and settles on flame grid 62 . Once this has occurred the reaction member 38 will now drive the generator continuously whilst the air/fuel mixture is available.
  • the engine runs efficiently under a continuous load, but is not designed to provide power against a varying load.
  • This type of engine is therefore most suitable for electricity generating and could for example be used in an electric car.
  • the engine can be used to generate electricity to recharge batteries whilst the vehicle is moving.
  • the engine is able to run so efficiently as a result of its lack of reciprocating parts and the use of air cooling which negates the requirement for a water pump and heat exchanger with their associated losses in engine efficiency.
  • an engine 130 has a compression fan 136 and a reaction member 138 .
  • a side casing 164 extends, at 176 , to partially enclose compression fan 136 .
  • the reaction member 138 also has further vanes 178 , which assist the entrainment of the cooling air, actively drawing it into the engine.
  • the vanes 160 are thickened at 180 so as to reduce the cross-sectional area, measured in a circumferential direction, of the space defined by two adjacent vanes, until the point were the frame front is to be ideally located, and then the cross-sectional area rapidly increases again.
  • This shape has the effect of acting as a single bluff-body as opposed to the multiple bluff-body resulting from the flame grid.
  • the fuel air mixture increases its velocity as cross-sectional area between the vanes decreases.
  • the space between the vanes is reduced so as to increase the velocity of the fuel such that it is faster than the flame speed of the fuel/air mixture and thus the flame front is maintained at this location.
  • reaction member 238 has further vanes 278 .
  • the length and location of these further vanes specifically compresses the cooling air to a pressure approximately equal to the pressure of the combustion gases resulting from the burning of the fuel air mixture as they leave the reaction member 238 .
  • Annexes I and II Attached, in Annexes I and II, are set point calculations for the temperatures and pressures throughout the process and an engine efficiency is also calculated.
  • the calculations in Annexe I are based on the assumption that the secondary compression, occurring in between the first sections 60 a of vanes 60 in reaction member 38 , is a ram compression.
  • the calculations in Annexe II are based on the assumption that the secondary compression is diffusion compression.
  • a slip factor of 0.835 is calculated for a 12 vane impeller.
  • the impeller peripheral speed U 1 is 460 m/s; Inlet temperature is 288° K.; Inlet pressure is 1.01 bar.
  • An isentropic efficiency of 81% is assumed (ie 90% impeller ⁇ 90% diffuser) over the whole compression process.
  • Air/fuel mixture leaves the compressor and enters the reaction wheel diffusion zone at a combined velocity of U 1 +U 2 and the velocity prior to combustion is U 3 relative to the reaction wheel.
  • the velocity of the mixture entering the diffuser is higher due to the rotation of the reaction wheel in the opposite direction to the impeller.
  • An isentropic efficiency of 81% is assumed for the whole of the compression process.
  • a combustion efficiency of 95% is assumed and the pressure drop is 5% of pressure P 3 .
  • the hot pressurised gas is to partially expand through the tangential nozzles, the reaction from which, will cause the reaction wheel to rotate and provide useful output power.
  • the power output reaction factor is adjusted iteratively to ensure that enough energy is left in the fluid to power the turbine. (The power output represents the useful shaft power output+the ram diffuser effort (section 2)+the cooling air delivery effort (section 5).) An isentropic efficiency of 90% is assumed for the reaction nozzles.
  • the hot pressurised gas is contained within the walls of the rotating reaction wheel Cooling air is delivered across the walls by radial vanes attached to the out side of the reaction wheel.
  • the vanes act like an impeller and are designed to deliver the cooling air at the same pressure as the hot combustion gases after partial expansion through the nozzles.
  • This cooling air is entrained by the high velocity of the primary combustion gases emerging at the reaction radius.
  • the total mass flow is estimated at 2.75 times the initial mass flow because an AFR of 60.5:1 (2.75 ⁇ 22) would give a cooler combustion temperature of 1150° K.
  • a slip factor of 0.835 is calculated for a 12 vane impeller.
  • the impeller peripheral speed U 1 is 460 m/s; Inlet temperature is 288° K.; Inlet pressure is 1.01 bar.
  • An isentropic efficiency of 81% is assumed (ie 90% impeller ⁇ 90% diffuser) over the whole compression process.
  • Air/fuel mixture leaves the compressor and enters the reaction wheel diffusion zone at a combined velocity of U 1 +U 2 relative to the diffuser.
  • the velocity of the mixture entering the diffuser is higher due to the rotation of the reaction wheel in the opposite direction to the impeller.
  • An isentropic efficiency of 81% is assumed (ie 90% impeller ⁇ 90% diffuser) over the whole compression process.
  • the hot pressurised gas is to partially expand through the tangential nozzles, the reaction from which, will cause the reaction wheel to rotate and provide useful output power.
  • the power output reaction factor is adjusted iteratively to ensure that enough energy is left in the fluid to power the turbine. (The power output represents the useful shaft power output+the ram diffuser effort (section 2)+the cooling air delivery effort (section 5).) An isentropic efficiency of 90% is assumed for the reaction nozzles.
  • the hot pressurised gas is contained within the walls of the rotating reaction wheel. Cooling air is delivered across the walls by radial vanes attached to the out side of the reaction wheel. The vanes act like an impeller and are designed to deliver the cooling air at the same pressure as the hot combustion gases after partial expansion through the nozzles. This cooling air is entrained by the high velocity of the primary combustion gases emerging at the reaction radius.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US10/470,361 2001-01-26 2002-01-28 Turbine engine Abandoned US20040154309A1 (en)

Priority Applications (1)

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US11/418,844 US20070068135A1 (en) 2001-01-26 2006-05-05 Engine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GBGB0102028.8A GB0102028D0 (en) 2001-01-26 2001-01-26 An engine and bearings therefor
GB0102028.8 2001-01-26
PCT/GB2002/000392 WO2002059469A1 (en) 2001-01-26 2002-01-28 Turbine engine

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US (2) US20040154309A1 (pl)
EP (1) EP1368560A1 (pl)
JP (1) JP4209680B2 (pl)
CA (1) CA2435116A1 (pl)
CZ (1) CZ20032007A3 (pl)
GB (1) GB0102028D0 (pl)
PL (1) PL373858A1 (pl)
WO (1) WO2002059469A1 (pl)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008091503A2 (en) * 2007-01-25 2008-07-31 Michael Nakhamkin Power augmentation of combustion turbines by extraction of additional expander airflow and injection thereof upstream of combustors
WO2008091502A3 (en) * 2007-01-19 2009-01-15 Michael Nakhamkin Power augmentation of combustion turbines by injection of cold air upstream of compressor
TWI604130B (zh) * 2016-07-18 2017-11-01 Orient Service Co Ltd 注氣式鼓風機
CN110319039A (zh) * 2019-06-24 2019-10-11 广东顺威精密塑料股份有限公司 一种均匀进气的离心风扇
US10598019B1 (en) * 2016-07-07 2020-03-24 Carl W. Kemp Turbine engine with a fire chamber and a helical fan
US11346366B2 (en) * 2019-02-11 2022-05-31 Carrier Corporation Rotating diffuser in centrifugal compressor
US11371428B2 (en) * 2018-06-12 2022-06-28 Gabrielle Engine Limited Combustion engine having a rotary compressor-combustor array

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EP1394386A1 (en) * 2002-08-06 2004-03-03 Politechnika Slaska Process for combusting fuels, in particular gas in an oxidizer of high temperature
NL1022803C2 (nl) * 2003-02-28 2004-08-31 Micro Turbine Technology B V Micro reactie turbine met geïntegreerde verbrandingskamer en rotor.
GB0608847D0 (en) * 2006-05-05 2006-06-14 Academy Projects Ltd An Engine
NL2000188C2 (nl) * 2006-08-18 2008-02-19 Micro Turbine Technology B V Reactieturbine met compressor.
DE102010055124A1 (de) * 2010-12-18 2012-06-21 Volkswagen Ag Energieversorgungseinrichtung
GB2526581A (en) * 2014-05-28 2015-12-02 Gabrielle Engine Ltd Combustion engine

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US1388707A (en) * 1918-10-01 1921-08-23 John O Heinze Turbine
US2579049A (en) * 1949-02-04 1951-12-18 Nathan C Price Rotating combustion products generator and turbine of the continuous combustion type
US3005311A (en) * 1957-08-08 1961-10-24 Frederick W Ross Gas turbine engine with combustion inside compressor
US3971209A (en) * 1972-02-09 1976-07-27 Chair Rory Somerset De Gas generators
US4625509A (en) * 1980-04-21 1986-12-02 Sheppard Sr Darrel J Combustion engine
US5282356A (en) * 1993-01-07 1994-02-01 Abell Irwin R Flywheel engine
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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008091502A3 (en) * 2007-01-19 2009-01-15 Michael Nakhamkin Power augmentation of combustion turbines by injection of cold air upstream of compressor
CN101225769B (zh) * 2007-01-19 2010-06-09 米歇尔·纳哈姆京 通过在压缩机上游注入冷空气而实现的燃气轮机功率增大
WO2008091503A2 (en) * 2007-01-25 2008-07-31 Michael Nakhamkin Power augmentation of combustion turbines by extraction of additional expander airflow and injection thereof upstream of combustors
WO2008091503A3 (en) * 2007-01-25 2009-01-08 Michael Nakhamkin Power augmentation of combustion turbines by extraction of additional expander airflow and injection thereof upstream of combustors
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JP2004520527A (ja) 2004-07-08
GB0102028D0 (en) 2001-03-14
US20070068135A1 (en) 2007-03-29
CA2435116A1 (en) 2002-08-01
CZ20032007A3 (cs) 2004-04-14
WO2002059469A1 (en) 2002-08-01
PL373858A1 (pl) 2005-09-19
EP1368560A1 (en) 2003-12-10

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